ROBINSON MAINTENANCE MANUAL R22 SERIES

not interfere with the swashplate travel. 10.120 a) Lift the swashplate boot so the uniball and slider tube may be observed. b) Pull the collective control full up. The uniball must not extend past the top of the slider tube more than .060 inch. If this occurs, adjust the Al21-5 and Al21-7 push pull tubes as follows: 1. Turn the upper rod ends of the Al21-5 and Al21-7 push-pull tubes in equally to lower the swashplate. 2. Recheck the uniball-slider tube clearance per Step b above. Main Rotor The main rotor is rigged by determining the average blade angle. Blade angle measurements are taken at the .75 radius of the main rotor (or 37.75 inches in from the blade tip). Issued 5/22/87 Page 10.3 ROBINSON MAINTENANCE MANUAL 8.3 INCHES I FULL LEFT_/\\ NEUTRAL TOTAL TRAVEL MCCELR22 VIEW LOOKING FWD CYCLIC CONTROL LATERAL NEUTRAL POSITION CYCLIC CONTROL FIGURE 10-1 CYCLIC CONTROL STICK NEUTRAL POSITION Page 10.4 Issued 5/22/87 DEC 2023 Chapter 10 Rigging, Track and Balance Page 10.5 FIGURE 10-3 A205 (-9 SHOWN) DIMENSIONS FOR SWASHPLATE SCISSORS FIGURE 10-2 LOWER SWASHPLATE CLEARANCE ROBINSON A281 Fitting MAINTENANCE MANUAL rTop of ball flush-to-0 . 060 inch above top of tube at full-up collective. - ~Tube 0 0 Lower (non-rotating) swashplate R22 SERIES Jo.g52 inch (Rigging blocks) .----------------____.__._._.___ \ MT146-1 Swashplate Rigging Blocks (2) l3 . 70 ± 0.03 inches - Upper (Rotating) 3.50 ± 0.03 inches - Lower (Non-rotating) 10.120 Main Rotor NOTE Refer to § 23-34 for push-pull tube rod end adjustment procedure. The main rotor is rigged by determining average blade angle. Blade angle is measured at 37.75 inches inboard from blade tip (main rotor 0.75 radius). Main rotor blade angles are measured using MT050-1 rigging fixture and a Kell-Strom KS113 propeller protractor or a comparable protractor (refer to Figure 10-4). Use following procedure to set up for rigging: 1. All main rotor flight control rod ends must meet Figure 2-1 radial play & axial play tolerance. 2. Rig swashplate per § 10.112. 3. Initially, adjust both pitch links to 6.82 inches length between rod end centers (final length is determined during autorotation rpm adjustment). 2. Verify A205 forks at swashplate are set to proper length per Figure 10-3. Lower fork assembly must be 3.50 ± 0.03 inches center-to-center and upper fork assembly must be 3.70 ± 0.03 inches center-to-center. 3. Level helicopter laterally and longitudinally via main rotor hub per § 18-12. 4. Place a tracking stick at end of one rotor blade and mark height of blade tip. Rotate rotor 180° and mark height of opposite blade tip. Teeter main rotor as necessary to obtain a main rotor track of ± 1 inch. 5. Using tape, conspicuously mark one MR blade tip. Place protractor atop MR hub parallel to teeter hinge bolt and facing tape-marked blade tip. Zero propeller protractor to main rotor hub. NOTE When measuring blade angles, protractor face or dial must always face marked blade tip to avoid doubling of instrument error. 6. Measure in from tip of each main rotor blade 37.75 inches and temporarily mark one blade with red color and opposite blade with blue color WARNING Use masking tape, grease pencil, or soft marker to mark rotor blades. Ball point pens or other sharp instruments can scratch blade skins, causing cracks and fatigue failure of blade. Page 10.6 Chapter 10 Rigging, Track and Balance DEC 2023 ROBINSON MAINTENANCE MANUAL R22 SERIES JUN 2024 Chapter 10 Rigging, Track and Balance Page 10.7 FIGURE 10-4 MAIN ROTOR BLADE RIGGING ROBINSON MAINTENANCE MANUAL R22 SERIES Propeller protractor MT050-1 Main Rotor Blade Rigging Fixture \ ' ~ - ~ ~ V p ~ 3 . nches from tip of main rotor blade Main rotor blade assembly Tape strip marking same blade tip protractor faced when set to zero. Page 10.8 Chapter 10 Rigging, Track and Balance JUN 2024 10.121 Cyclic Travel Rigging 1. Determine if A958-1 bellcranks are installed in cyclic pivot assembly (ref. Figure 8-2A; original equipment on helicopter S/N 0256, 0301, 0350, 0351, and 0357 & subsequent). 2. Refer to Figure 10-1. Place collective control full down. Place cyclic control in neutral position laterally and hold against forward stop. NOTE Sand bags may be used to secure cyclic control against forward stop to ensure it will not move. 3. Rotate blades so pitch links are aligned with longitudinal axis of helicopter. Place tracking stick at tip of one blade for reference when rotating rotor. 4. Forward longitudinal cyclic: a. Refer to Figure 10-4. Measure blade angles and record below. Rotate rotor 180° and record blade angles below. Adjust blade angles per step 4.b. BLUE BLADE RED BLADE Pitch link aft ° Pitch link aft ° Pitch link forward + ° Pitch link forward + ° = ° = ° ÷ 2 = ° ÷ 2 = ° 10.5°/11.0° required, if A958-1 bellcranks are installed. 8.3°/8.8° required, if A175-1 bellcranks are installed. b. Adjust aft A121-5 push-pull tube at swashplate (one full turn = 0.42°) or both forward A121-7 push-pull tubes at swashplate (both must be adjusted exact same amount), as required to obtain required blade angle averages. 5. Refer to Figure 10-1. Place cyclic control in neutral position laterally and hold against aft stop. ROBINSON MAINTENANCE MANUAL R22 SERIES JUN 2024 Chapter 10 Rigging, Track and Balance Page 10.9 10.121 Cyclic Travel Rigging (continued) 6. Aft longitudinal cyclic: a. Refer to Figure 10-4. Measure blade angles and record below. Rotate rotor 180° and record blade angles below. Adjust blade angles per step 6.b. BLUE BLADE RED BLADE Pitch link aft ° Pitch link aft ° Pitch link forward + ° Pitch link forward + ° = ° = ° ÷ 2 = ° ÷ 2 = ° 8.5°/9.5°required. b. Adjust aft A121-5 push-pull tube at swashplate (one full turn = 0.42°) or both forward A121-7 push-pull tubes at swashplate (both must be adjusted exact same amount), as required. NOTE If adjustment is required to obtain aft cyclic control blade angles, forward cyclic must be rechecked. 7. Refer to Figure 10-1. Place cyclic control in neutral position longitudinally (mid- travel) and hold cyclic against left stop. 8. Rotate rotor until pitch links are aligned with lateral axis of helicopter. Place tracking stick at tip of one blade for reference when rotating rotor. 9. Left lateral cyclic: a. Refer to Figure 10-4. Measure blade angles and record below. Rotate rotor 180° and record blade angles below. Adjust blade angles per step 9.b. BLUE BLADE RED BLADE Pitch link right ° Pitch link right ° Pitch link left + ° Pitch link left + ° = ° = ° ÷ 2 = ° ÷ 2 = ° 9.0°/9.5° required. b. Adjust right or left (forward) A121-7 push-pull tube at swashplate (one full turn = 0.6°), as required. ROBINSON MAINTENANCE MANUAL R22 SERIES Page 10.10 Chapter 10 Rigging, Track and Balance JUN 2024 10.121 Cyclic Travel Rigging (continued) 10. Refer to Figure 10-1. Place cyclic control in neutral position longitudinally (mid travel) and hold against right stop. 11. Right lateral cyclic: a. Refer to Figure 10-4. Measure blade angles and record below. Rotate rotor 180° and record blade angles below. Adjust blade angles per step 11.b. BLUE BLADE RED BLADE Pitch link right ° Pitch link right ° Pitch link left + ° Pitch link left + ° = ° = ° ÷ 2 = ° ÷ 2 = ° 5.5°/6.0° required. b. Adjust right or left (forward) A121-7 push-pull tube at swashplate (one full turn= .6°) as required. NOTE If adjustment is required to obtain right cyclic control blade angles, left cyclic must be rechecked. 12. Perform collective travel rigging per § 10.122. ROBINSON MAINTENANCE MANUAL R22 SERIES DEC 2023 Chapter 10 Rigging, Track and Balance Page 10.11 10.122 Collective Travel Rigging 1. Rotate main rotor to align pitch links with longitudinal axis of helicopter. Place tracking stick at tip of one blade for reference when rotating rotor. 2. Refer to Figure 10-1. Place cyclic control in neutral position or install MT376-1 rigging blocks. Place collective control full down. Apply cyclic and collective friction. 3. Collective full down: a. Refer to Figure 10-4. Measure blade angles and record below. Rotate rotor 180° and record blade angles below. Adjust blade angles per steps 3.b. BLUE BLADE RED BLADE Pitch link forward ° Pitch link forward ° Pitch link aft + ° Pitch link aft + ° = ° = ° ÷ 2 = ° ÷ 2 = ° 2°±0.5° nose up required. 2°±0.5° nose up required. b. Adjust pitch links so blue blade and red blade measurements are within 0.2° of each other when each blade pitch link is in forward position, and when each pitch link is in aft position. NOTE Final collective down blade angles are determined by autorotation RPM requirements per § 10.250. 4. Raise collective control to full up position. Apply collective friction. 5. Collective full up: a. Refer to Figure 10-4. Measure blade angles and record below. Rotate rotor 180° and record blade angles below. BLUE BLADE RED BLADE Pitch link forward ° Pitch link forward ° Pitch link aft + ° Pitch link aft + ° = ° = ° ÷ 2 = ° ÷ 2 = ° 14°±0.5° nose up required. 14°±0.5° nose up required. 6. Verify top of swashplate ball is flush-to-0.060 inch above top of tube per Figure 10-2. 7. Perform track and balance per § 10.200. ROBINSON MAINTENANCE MANUAL R22 SERIES Page 10.12 Chapter 10 Rigging, Track and Balance DEC 2023 10.130 Tail Rotor Flight Controls NOTE Refer to § 23-34 for push-pull tube rod end adjustment procedure. 10.131 Pedals 1. Refer to Figure 10-5. Insert a 3/16-inch diameter rigging pin (a long AN3 or NAS6603 bolt suffices) thru hole in right-side keel panel and rigging pin holes in A317-1 bellcrank. 2. Adjust A121-9 and -11 push-pull tubes as required to obtain a dimension of 2.90 ± 0.03 inches from each pedal to stops located on each side of forward console. Remove rigging pin (or bolt, as applicable). 10.132 A316-1 Bellcrank 1. Refer to Figure 10-5. Place left pedal against forward stop. 2. Adjust vertical A121-13 push-pull tube to obtain a minimum of 0.060 inch between A316-1 bellcrank arm and vertical firewall control tunnel. 10.133 A331-1 Bellcrank Place right pedal against forward stop. Adjust horizontal A121-15 push-pull tube to obtain a minimum clearance of 0.100 inch between A331-1 bellcrank and actuator gearbox housing (See Figure 10-6). ROBINSON MAINTENANCE MANUAL R22 SERIES ROBINSON MAINTENANCE MANUAL MOOELR22 Al21-15 P/P TUBE A316-l BELLCRANK A121-13 P/P TUBE PEDAL STOPS A121-ll P/P TUBE ______ _J Issued 5/22/87 FIGURE 10-5 PEDAL CONTROL INSTALLATION --\_ HORIZ. FIREWALL 3/16 IN. DIAM. RIGGING PIN, NEUTRAL POSIT ION Page 10.13 ROBINSON MAINTENANCE MANUAL MOOELR22 Page 10 .14 Al21-15 P/P TUBE \ \ \ FUSELAGE ROD END OTHER SIDE A331-l BELLCRANK ~ ~ ~ I ...... ~-j~ TAIL FRAME ASSY. 1\ ........ -........ I / \ 1 :- CLEARANCE ' I 11 I ' I I , ,., '-M....-:,.-r-----------~....i P/P TUBE \ ' TAIL CONE VIEW LOOKING DOWN FIGURE 10-6 A331 BELLCRANK INSTALLATION Issued 5/22/87 ROBINSON MAINTENANCE MANUAL MO □ EL R22 10.133 A 120-3 Bellcrank (cont'd) NOTE Actuator must be disengaged when adjusting A331 bellcrank to check closest point. Place left pedal against its stop and check for clearance between A331-1 bellcrank and tailcone. 10.134 A 120-1 Bellcrank With tail rotor pedals in neutral position, adjust A 121-17 push-pull tube as required to obtain a nominal dimension of 4.85 inches between bellcrank arm center line and machined face of tailcone casting (see Figure 1 0- 7). 10.135 Tail Rotor Pitch Links If applicable, adjust pitch links to a dimension of 2.360 inches between rod end centers (See Section 8.570). 10.140 Tail Rotor Rigging WARNING Both pitch links must be same part number (same type and material). Mixing one-piece with adjustable-length pitch links is prohibited. Mixing steel one-piece with aluminum one-piece pitch links is prohibited. 1. Set up: a. Ensure removable pedals are installed. b. Level rotorcraft per Section 1 .220 Method 2, Main Rotor Hub. c. Rotate tail rotor until forward blade is parallel to tailcone. d. Tape a tracking stick to tailcone at tip of forward blade. NOTE A tracking stick can be made using a 1 inch by 12 inch strip of aluminum with a 90° bend 2 inches from one end. e. Place left pedal against its stop. Using a tip drain hole as a reference, first mark tracking stick where blade tip passes stick. f. Using clutch shaft so teeter angle is not disturbed, rotate tail rotor 180° until opposite blade tip drain hole is aligned with tracking stick. Mark stick. Change 26: APR 2007 10.15 ROBINSON MAINTENANCE MANUAL MODEL R22 10.140 Tail Rotor Rigging (cont'd) 10.16 g. Adjust teeter of tail rotor to position blade tip mid point between marks. This will be the left-pedal tacking mark. Rotate tail rotor and check that the blades track. Repeat above procedure as necessary to track tail rotor within 0.125 inch. 2. Measure tail rotor blade angles as follows: a. Using a soft marker or grease pencil mark each blade as red or blue. b. Measure in from each blade tip 5.25 inches (0. 75 radius) and place a mark chord wise on each blade at this point (soft marker or grease pencil). c. Have some one hold forward blade tip at left pedal track mark. d. Place MT050-2 rigging fixture on aft blade inboard side. NOTE The MT050-2 fixture must be centered on 0. 75 radius mark. e. Using a propeller protractor measure blade angle and record below. Rotate tail rotor 180° and record opposite blade angle. Blue Blade Red Blade -+-2 Pedals Full Left 0 nose right --- + 0 nose right --- 0 0 (19.0°/19.5° required) Change 26: APR 2007 I ' ROBINSON MAINTENANCE MANUAL Al48-l TAILCONE CLOSURE BULKHEAD AFT MACHINED FACE MOOEL R22 t\::::::============~! r---,..;--,~ A120-l BELLCRANK -- rl - . Al21-17 P/P TUBE l (-~:- ·: o' .. - • PROPELLER PROTRACTOR ~ TAIL ROTOR ASSEMBLY~ __ C .. 7 MTOS0-2 ru-rn. · ~;;;~~~ ___r-- - L__ . - --, • 1/ --_ -~~ ~ -- . -._______.::_~~::.J ~ TRACKING STICK rS.25"-1 DISTANCE FROM THE END OF THE TAIL ROTOR BLADE FIGURE 10-7 Al20-l BELLCRANK INSTALLATION Issued 5/22/87 Page 10.17 ROBINSON MAINTENANCE MANUAL MOOEL R22 10.140 Page 10.18 Tail Rotor Rigging (cont'd) ICAUTION l For acceptable track, differences between Blue and Red blade angles must not exceed .4 degrees. If the blade angles cannot be ad- justed to within .4 degrees of each other using the pitch links they should be replaced. NOTE Pitch link jamnuts must be tight to ensure accurate blade angle measurements. f) Adjustment of the blade angles is made using the rod ends of the Al21-17 push-pull tube. One full turn of the rod end will change the blade angles .42 degrees. Adjust the rod end as ne- cessary to obtain 19.0 to 19.5 degrees. g) Place the right pedal against its stop. Measure the blade angles and record below. NOTE When pedal is placed against the right stop, a new tracking mark must be placed on the track stick as the tip path will change due to blade angle change. Pedals Full Blue Blade 0 nose Red Blade + 0 nose 07"2= Right left left 0 (9.6/10.6 deg. req'd) h) Adjust the A121-17 push-pull tube as necessary to obtain blade angles of 9.6 to 10.6 degrees. NOTE If adjustment is required to ob- tain right pedal blade angles, the left pedal angles must be rechecked. Issued 5/22/87 ROBINSON MAINTENANCE MANUAL MOOELR22 10.140 Tail Rotor Rigging (cont'd) i) If the blade angle range, for left and right pedal settings, cannot be obtained using the above procedure, this indicates the pedal travel is either too great or too small. Use the following procedure to check and adjust pedal travel: 1) 2) 3) Add the right and left pedal angles together. If the total is less than 28.6° the pedal total travel is too 8mall. If the total is greater than 30.1 the total travel is too great. To increase the total travel, lengthen the Al21-9 and -11 push-pull tubes attached to the tail rotor pedals. To decrease the total travel, shorten the Al21-9 and -11 push-pull tubes. NOTE These changes should be made in 1/2 turn increments of the push- pull tube rod ends. 4) Recheck the tail rotor blade angles per steps e through h above. j) Ensure all rod ends are installed properly by checking the push-pull tube witness holes. Tight- en all rod end palnuts and jamnuts. Torque stripe all jamnuts. 10.150 Throttle Correlation Rigging (See Figure 10-8) a) For inservice check and adjustment, perform the following: 1) 2) Issued 5/22/87 Rotate the throttle in "off" direction through the overtravel spring to the positive stop. Holding the throttle tight against the stop, raise collective to full up stop while ob- serving throttle bellcrank on carburetor. Throttle bellcrank should just barely start to move when the collective up stop is reached. Page 10.19 ROBINSON MAINTENANCE MANUAL MODELR22 COLLECTIVE Adjust A327-1 Overtravel Spring Assembly to fit following geometry with no spring compression: Collective full up, throttle twist grip rotated full closed, A609-2 Arm at dimension shown. Then, adjust A336 or B364 Push-Pull Tube to fit with carburetor arm just off idle stop (0.02-0.05 inch movement at rod end bolt) (push-pull tube must be readjusted whenever idle stop is adjusted). Select A336-1 or -2 push-pull tube, or install A 130-54 spacer(s), as required to obtain proper adjustment. OVERTRAVEL SPRING IDLE RPM ADJUSTMENT SCREW CONNECTING ROD CARBURETOR A336-1 or -2 PUSH-PULL TUBE (0-320 engine) B364-1 PUSH-PULL TU~E (0-360 engine) CARBURETOR BORE CENTERLINE '~ ---~ f~-- 0 CARBURETOR THROTTLE LEVER Throttle lever to be 58±7 .5 degrees at full open (set to nearest tooth) Connect to middle hole FIGURE 10-8 THROTTLE CORRELATION RIGGING Page 10.20 Change 22: MAR 2004 OCT 2018 Chapter 10 Rigging, Track and Balance Page 10.21 10.150 Throttle Correlation Rigging (continued) NOTE Before adjusting throttle connecting rod, ensure idle RPM and engine shimming are correctly adjusted per §§ 2.210 and 6.130. 3. See Figure 10-8. If required, adjust length of throttle connecting rod for 0.020–0.050 inch gap between carburetor butterfly bellcrank and idle RPM adjustment screw when performing step 2. 4. Tighten jamnut(s), check witness holes, and safety wire rod end, as required. (Note: If A933-3 rod end is installed, B330-7 palnut is required.) 10.200 Track and Balance 10.210 Equipment Requirements NOTE Calibrate track and balance equipment per manufacturer’s recommendation, at least once a year, or if equipment is dropped, misused, or calibration is suspect. NOTE The Chadwick-Helmuth Vibrex system, the TEC ACES system, the Dynamic Solutions Systems’ MicroVib system, or equivalent equipment is required to perform dynamic rotor balancing and in-flight track checks. 10.220 Equipment Installation 10.221 Main Rotor Equipment Installation NOTE Use the following track & balance procedures in conjunction with approved equipment manufacturer’s balancing instructions. CAUTION Cable security is critical; helicopter will be flown at VNE. a. Refer to Figure 10-9A. Using appropriate hardware, attach brackets to vibration transducer and attach assembly A359-1 panel as shown. Remove removable controls. b. Install magnetic pickup bracket onto swashplate if not previously installed. ROBINSON MAINTENANCE MANUAL R22 SERIES Intentionally Blank Page 10.22 Chapter 10 Rigging, Track and Balance OCT 2018 ROBINSON MAINTENANCE MANUAL R22 SERIES ROBINSON MAINTENANCE MANUAL MCCELR22 10.221 10.222 Main Rotor Equipment Installation (cont'd) IWARNING I Ensure attachment bolts are torqued to 100 in.-lbs plus nut drag. The PT121 bracket will re- main installed for inflight track and balance. c) Install the 3030 magnetic pickup onto the PT121 bracket. Set the interrupter pickup gap to .030" ± .010". d) Attach the 3319-1 cable to the magnetic pickup. Pull collective stick full up and cyclic stick full left. Secure the cable to the mast fairing with duct tape. Route the cable to the lower front of the left door frame. Secure the cable every 12" with duct tape. ICAUTION I Security of the cable is essen- tial as the helicopter will be flown at Vne. e) Attach the 4296-1 cable to the accelerometer mounted on the console. Secure with duct tape. I CAUTION I Ensure the cable cannot become tangled with tail rotor pedals. f) Attach the cables to the balancer and secure ex- cess cable to the bracket in front of the left seat. g) Apply the 4270 target tapes to the main rotor blades per Figure 10-9. Tail Rotor Equipment Installation (See Figure 10-9C) a) Install the 4177 accelerometer under the top forward tail rotor gearbox output cartridge attachment bolt. Connector end of accelerometer must point up. b) Connect the 4296-2 cable to the accelerometer. Wrap cable around the tailcone several times towards the forward end. Secure with duct tape. Change 6: 28 JUL 89 Page 10.23 I ROBINSON MAINTENANCE MANUAL MDDELR22 w U1 ....... 3 z c:::( Cl... U1 Page 10.24 TARGET WIDTH DI t CHORDWISE t TARGET LENGTH t::::=:::===========1==--=---,---J' FIGURE 10-9 MAIN ROTOR TARGET PATCH LOCATION Change 19: 30 JUN 99 ROBINSON MAINTENANCE MANUAL MCCELR22 STROBEX 0 ~)~j_t~-BA=LAN=C-ER~~~~~~-=rr __;,.~--'-{·-.r--- ~~~ DUCT TAPE ~, ~ 4177 ACCELEROMETER I 3030 AGNETIC PICKUP I I i i ,,,, .': RUN CABLE UNDER CARPET ~~~-· ENSURE THAT CABLE ·-:• IS ROUTED BEHIND / THE LEFT PEDAL STOP ~ (IF EQUIPPED) TO PREVENT CABLE FROM BEING CAUGHT PT121 BRACKET BETWEEN PEDAL AND CONSOLE FIGURE 1O-9A MAIN ROTOR EQUIPMENT INSTALLATION Issued 5/22/87 Page 10.25 ROBINSON MAINTENANCE MANUAL MOCELR22 CHORD (COUNTER) WEIGHTS DOUBLE INTERRUPTER INSTALLED HERE FIGURE 10-98 DOUBLE INTERRUPTER INSTALLATION SLIDER- TUBE 0 o/ -. -- ----- C INTERRUPTER INSTALLED HERE If the interrupters are installed as shown above the Main Rotor Balancing Chart will be out of phase. Using a model 135M-10 Strobex with the interrupters installed per above drawing and using Doubler Interrupter Logic on the Balance Box, the Forward Blade must be relabeled as Aft. The Aft Blade must be relabeled Forward. Adding and subtracting chord weights and rotor head shifts would also be out of phase. To use the Main Rotor Track and Balance Chart correcting it, you must reverse the interrupters. double interrupter must be on the opposite side of driveshaft as the Chord (counter) weights. without The the Page 10.25A Change 6: 28 JUL 89 ROBINSON MAINTENANCE MANUAL MCCELR22 This page intentionally left blank. Change 6: 28 JUL 89 Page 10.25B ROBINSON MAINTENANCE MANUAL MOOELR22 DUCT ,...., A TAPE ~ r<i:=:c·· ➔.......--sTROBEX ~e4296-2 ~ 4177 ACCELEROMETER /\ CABLE ~ FIGURE 10-9C TAIL ROTOR EQUIPMENT INSTALLATION Page 10.26 Change 6: 28 JUL 89 ROBINSON MAINTENANCE MANUAL MODEL R22 10.222 Tail Rotor Equipment Installation (cont'd) WARNING Tail rotor balancing equipment must be removed for flight. FIGURE 10-9C TAIL ROTOR BALANCING EQUIPMENT INSTALLATION Change 25: JUN 2006 10.26A ROBINSON MAINTENANCE MANUAL MODEL R22 10.26B 10.222 Tail Rotor Equipment Installation (cont'd) I I I I _,.- .,.- 1$ (VIEW LOOKING FORWARD) WARNING PHOTOCELL (PIVOT PHOTOCELL MOUNTING BRACKET SO PHOTOCELL BEAM ALIGNS WITH TARGET TAPE WHEN TAPE IS AT 12 O'CLOCK POSITION.) Tail rotor balancing equipment must be removed for flight. FIGURE 10-9D TAIL ROTOR PHOTOCELL INSTALLATION Change 25: JUN 2006 10.222 Tail Rotor Equipment Installation (continued) c. Place a target tape on tail rotor hub inboard surface approximately 1 inch in from on blade’s outboard attach bolt. CAUTION Ensure cables cannot become entangled in tail rotor. d. Refer to Figures 10-9C and 10-9D. Install and secure photocell and mounting bracket to velocimeter bracket as shown. Connect extension cable to photocell and wrap cable several times around tailcone and secure with duct tape. e. Connect cables to balancer. NOV 2020 Chapter 10 Rigging, Track and Balance Page 10.27 ROBINSON MAINTENANCE MANUAL R22 SERIES Page 10.28 Chapter 10 Rigging, Track and Balance NOV 2020 BALANCE TRACK (KNOTS) CLOCK IPS HOVER 50 60 70 80 90 100 I I I I I I I I I I I I I I Adjustment: CLOCK IPS HOVER 50 60 70 80 90 100 I I I I I I I I I I I I I I Adjustment: CLOCK IPS HOVER 50 60 70 80 90 100 I I I I I I I I I I I I I I Adjustment: CLOCK IPS HOVER 50 60 70 80 90 100 I I I I I I I I I I I I I I DATE SERIAL NO. PAGE FIGURE 10-10 MAIN ROTOR TRACK AND BALANCE CHART ROBINSON MAINTENANCE MANUAL * See text for substitutions . R22 SERIES Tip Weights ~ I ll FORWARD BLADE (~\ '. I /JI 1-----+-----+------+--------1---+-----+-----+-----+-------<I Chmd A,m -~-....D/1 Weight AFT I BLADE I ~Tip Weights NOV 2020 Chapter 10 Rigging, Track and Balance Page 10.29 10.230 Main Rotor Track and Balance Procedure NOTE Prior to installing balancing equipment, verify blades are clean and smooth, rod ends & spherical bearings & scissors play are within limits, correct upper (rotating) scissors friction, correct swashplate tilting friction, and coning hinge frictions. Verify interrupter is opposite chord arm. In-flight track and balance is accomplished using the following testing and adjustment sequence: 1. Check main rotor track in a hover and record data. Adjust track by shortening high blade pitch link per § 10.232 to bring track within 0.25 inch. 2. Check main rotor balance in a hover and record data. Adjust balance as indicated by main rotor balance chart to within 0.2 IPS (inches per second). 3. Fly helicopter at 50, 60, 70, 80, 90, and 100 knots. Check track at each airspeed and record. WARNING Do not exceed VNE of helicopter when checking in-flight track. 4. Make slight tab adjustment to correct for a climbing blade by bending trim tab down per § 10.233. 5. Repeat steps 3 & 4 as required until track is within 3/8 inch at all airspeeds. 6. Readjust main rotor balance in a hover to no greater than 0.2 IPS. 7. Check autorotational RPM per § 10.250. Adjust as required. 8. Evaluate collective trim, longitudinal cyclic trim, and lateral cyclic trim. Adjust as required. 9. Check main rotor balance in a hover. Verify no greater than 0.2 IPS. Adjust as required. ROBINSON MAINTENANCE MANUAL R22 SERIES FIGURE 10-11 MAIN ROTOR BLADE TIP Page 10.30 Chapter 10 Rigging, Track and Balance NOV 2020 ROBINSON MAINTENANCE MANUAL (2) NAS1351N3-10P Screws ,_ Install using A257-9 anti-seize on '-4---"--"~ "7~-'--"-"'"~~.c..-""1--r-~,::i--- 1 threads; special torque to 40 in.-lb. Tip weights (Ref) (2) A722-4 Screws R22 SERIES Install using A257-9 anti-seize on threads; special torque to 40 in.-lb. A300-3 Cover 10.231 Main Rotor Balance Adjustments WARNING A rotor which is smooth after balancing but goes out of balance within a few flights is suspect and must be examined by RHC before further flight. A. Tip Weights (Spanwise Balance Adjustment) 1. Remove screws securing tip cover to blade. Balance rotor assembly spanwise by adjusting tip weights as required per Figure 10-10. Washers may be trimmed. Refer to Figure 10-11. Apply light coat A257-9 anti-seize to threads and install screws securing tip weights to blade; special torque screws to 40 in.-lb. Apply light coat A257-9 anti-seize to threads and install screws securing tip cover to blade; special torque screws to 40 in.-lb. (1) AN960-10 or NAS1149F0363P Washer = (2) AN960-10L or NAS1149F0332P Washers (1) A298-2 Weight = 0.034 lb (1) A298-3 Weight = 0.009 lb B. Teeter Hinge Bolt Shims (Chordwise Balance Adjustment – Coarse Adjustment) 1. Remove and discard teeter hinge nut cotter pin. Remove nut, thrust washer, and any shims. 2. Have two people cone the main rotor blades. Push out teeter hinge bolt (and any shims) with another bolt. 3. Balance rotor assembly chordwise by moving (or exchanging) existing teeter hinge shims to other side of bolt (under head or under nut) as required per Figure 10-10. Install teeter hinge bolt per § 26-10. C. Chord Arm Weight (Chordwise Balance Adjustment – Fine Adjustment) 1. Balance rotor assembly chordwise by adjusting chord arm weights or washers per Figure 10-10. Total weight not to exceed two A255-2 weights (or equivalent). (1) A255-1 Weight = (8) AN970-4 Washers (1) A255-2 Weight = (3) A255-1 Weights NOV 2020 Chapter 10 Rigging, Track and Balance Page 10.31 ROBINSON MAINTENANCE MANUAL R22 SERIES FIGURE 10-12A A258-5 MAIN ROTOR PITCH LINK Page 10.32 Chapter 10 Rigging, Track and Balance NOV 2020 ROBINSON MAINTENANCE MANUAL Medium Length Adjustment Upper Rod End Only ------ • One-half turn of upper rod end changes blade track 0.25 inch • One-half turn of upper rod end changes blade angle 0.24° Fine Adjustment-------- Barrel Assembly Only • One-half turn of barrel changes blade track 0 . 125 inch • One-half turn of barrel changes blade angle 0 . 12 ° Coarse Length Adjustment ------ Lower Rod End Only • One-half turn of lower rod end changes blade angle 0. 36 ° R22 SERIES ...,.___ Rod End (Upper, attaches to pitch horn) =~--Jam nut Torque stripe (typical) ~----Witness Hole After any adjustment, verify rod end threaded shank blocks pas- sage of 0.020-inch dia lockwire. ---- Barrel assembly (includes self-locking thread insert; lockwire is not required) ~ Witness Hole After any adjustment, verify rod end threaded shank blocks pas- sage of 0 . 020-inch dia lockwire . 21 FKF-616 Jam nut Rod End (Lower, attaches to swashplate) 10.232 Main Rotor Pitch Link Adjustment A. Main Rotor Blade Pitch Link NOTE Shorten high pitch blade when adjusting track in a hover. NOTE During rigging, adjust both pitch links exactly the same for collective adjustments. 1. For fine adjustment: a. A258-5 Pitch Link: Adjust barrel assembly only per the following steps: i. Refer to Figure 10-12A. Using backup wrench on barrel assembly, loosen 21FKF-616 nut at lower rod end, and upper rod end palnut and jam nut. ii. Rotate barrel assembly to shorten or lengthen pitch link as required. One-half turn of barrel changes blade track approximately 0.125 inch. One-half turn of barrel changes blade angle approximately 0.12°. For finer adjustment, rotate less than one-half turn as required. iii. Refer to Figure 2-1. Verify rod end threaded shank blocks passage of 0.020-inch diameter lockwire through barrel assembly witness holes. iv. Position rod ends to allow as much pitch link rotation as possible without binding. Using backup wrench on barrel assembly, special torque 21FKF-616 nut per § 23-33, and standard torque upper rod end jam nut and palnut per § 23-32. v. Repeat steps on opposite pitch link as required; torque stripe per Figure 2-1. b. A258-1 Pitch Link: Adjust fitting only per the following: i. Refer to Figure 10-12B. Cut and discard pitch link assembly safety wire. Using backup wrench on link assembly, loosen 21FKF-616 nut; using backup wrench on fitting, loosen upper rod end palnut and jam nut. ii. Rotate fitting to shorten or lengthen pitch link as required. One-half turn of fitting changes blade track approximately 0.125 inch. One- half turn of fitting changes blade angle approximately 0.12°. For finer adjustment, rotate less than one-half turn as required. iii. Refer to Figure 2-1. Verify rod end threaded shank blocks passage of 0.020-inch diameter lockwire through pitch link witness holes. iv. Using backup wrench on link assembly, special torque 21FKF-616 nut per § 23-33. Using backup wrench on fitting, standard torque upper rod end jam nut and palnut per § 23-32. Safety fitting to link assembly using 0.032-inch diameter lockwire. v. Repeat steps on opposite pitch link as required; torque stripe per Figure 2-1. NOV 2020 Chapter 10 Rigging, Track and Balance Page 10.32A ROBINSON MAINTENANCE MANUAL R22 SERIES FIGURE 10-12B A258-1 MAIN ROTOR PITCH LINK Page 10.32B Chapter 10 Rigging, Track and Balance NOV 2020 ROBINSON MAINTENANCE MANUAL Medium Length Adjustment ------ Upper Rod End Only • One-half turn of upper rod end changes blade track 0 .25 inch • One-half turn of upper rod end changes blade angle 0 . 24° Fine Adjustment-------- Fitting Only • One-half turn of fitting changes blade track 0. 125 inch • One-half turn of fitting changes blade angle 0. 12 ° Coarse Length Adjustment ------ Link Assembly Only • One-half turn of link assembly changes blade angle 0.36° R22 SERIES •...,..,__ Rod End (Upper, attaches to pitch horn) ..--- Palnut Jam nut :.........---Torque stripe (typical) ,~;.---- Witness Hole After any adjustment, verify rod end threaded shank blocks passage of 0.020-inch dia lockwire. Fitting 21 FKF-616 Nut --......--Witness Hole (Ref) P-1....- Safety fitting to link assembly using 0.032-inch dia lockwire. --- Link Assembly 10.232 Main Rotor Pitch Link Adjustment (continued) A. Main Rotor Blade Pitch Link (continued) 2. For medium length adjustment, adjust upper rod end per the following: a. Refer to Figure 10-12A or 10-12B. Using backup wrench on barrel assembly or fitting, loosen upper rod end palnut and jam nut. Remove hardware securing rod end to pitch horn. b. Rotate upper rod end to shorten or lengthen pitch link as required. One-half turn of upper rod end changes blade track approximately 0.25 inch. One- half turn of upper rod end changes blade angle by approximately 0.24°. c. Refer to Figure 2-1. Verify rod end threaded shank blocks passage of 0.020- inch diameter lockwire through barrel asssembly (upper), or fitting, witness hole. Install hardware securing rod end to pitch horn and standard torque fasteners per § 23-32. d. Position rod ends to allow as much pitch link rotation as possible without binding. Using backup wrench on barrel assembly or fitting, standard torque upper rod end jam nut and palnut per § 23-32. e. Repeat steps on opposite pitch link as required; torque stripe per Figure 2-1. 3. For coarse length adjustment: a. A258-5 Pitch Link: Adjust lower rod end per the following: i. Refer to Figure 10-12A. Using backup wrench on barrel assembly, loosen 21FKF-616 nut at lower rod end. Remove hardware securing lower rod end to swashplate. ii. Rotate lower rod end to shorten or lengthen pitch link as required. One- half turn of lower rod end changes blade angle by approximately 0.36°. iii. Refer to Figure 2-1. Verify rod end threaded shank blocks passage of 0.020-inch diameter lockwire through barrel asssembly (lower) witness hole. Install hardware securing rod end to swashplate and standard torque fasteners per § 23-32. iv. Position rod ends to allow as much pitch link rotation as possible without binding. Using backup wrench on barrel assembly, special torque 21FKF-616 nut per § 23-33. v. Repeat steps on opposite pitch link as required; torque stripe per Figure 2-1. NOV 2020 Chapter 10 Rigging, Track and Balance Page 10.32C ROBINSON MAINTENANCE MANUAL R22 SERIES 10.232 Main Rotor Pitch Link Adjustment (continued) A. Main Rotor Blade Pitch Link (continued) 3. For coarse length adjustment (continued): b. A258-1 Pitch Link: Adjust link assembly per the following: i. Refer to Figure 10-12B. Cut and discard pitch link assembly safety wire. Using backup wrench on link assembly, loosen 21FKF-616 nut. Remove hardware securing lower rod end to swashplate. ii. Rotate link assembly to shorten or lengthen pitch link as required. One- half turn of link assembly changes blade angle by approximately 0.36°. iii. Refer to Figure 2-1. Verify rod end threaded shank blocks passage of 0.020-inch diameter lockwire through link assembly witness hole. Install hardware securing rod end to swashplate and standard torque fasteners per § 23-32. iv. Position rod ends to allow as much pitch link rotation as possible without binding. Using backup wrench on link assembly, special torque 21FKF-616 nut per § 23-33. Safety fitting to link assembly using 0.032-inch diameter lockwire. v. Repeat steps on opposite pitch link as required; torque stripe per Figure 2-1. Page 10.32D Chapter 10 Rigging, Track and Balance NOV 2020 ROBINSON MAINTENANCE MANUAL R22 SERIES Intentionally Blank NOV 2020 Chapter 10 Rigging, Track and Balance Page 10.32E ROBINSON MAINTENANCE MANUAL R22 SERIES FIGURE 10-13 MAIN ROTOR BLADE TRIM TAB ADJUSTMENT Page 10.32F Chapter 10 Rigging, Track and Balance NOV 2020 ROBINSON MAINTENANCE MANUAL R22 SERIES Main rotor blade --- Main rotor blade trailing edge Using felt-tip marker, draw a line on main rotor blade trim tab upper surface, in-line with blade trailing edge . ----------------~!_________t~--------M-a-in-ro_t_o_r-I-d-e-tr-im_t_a_b ___ /Gage must contact tab trailing edge or tab is bent beyond limit . MT526 Bending tool Tighten bending tool bolt to bend tab; do not use tool as a lever. Mark line with a measuring point in the center of tab (approximate) . MT352-1 Gage Position gage chordwise across blade upper surface and tab trailing edge . Zero dial indicator on measuring point . @ 0 L Ma;n rotor blade tramng edge t Bolt ~ Stop (2) Main rotor blade Double-rib side of tool should contact tab upper surface to bend tab down. 0 tSlide bending tool over tab until tool stops contact blade trailing edge . Main rotor blade 10.233 Main Rotor Blade Trim Tab Adjustment NOTE To correct for a "climbing" blade condition (blade spread that exceeds 3/8 inch with forward airspeed), bend high blade trim tab down. CAUTION Do not use other helicopter manufacturers' trim tab bending tools. Use of these tools will damage Robinson blades. CAUTION MT352-1 gage must contact trim tab trailing edge. If gage does not contact tab trailing edge, tab is bent beyond limit. CAUTION Tighten MT526-1 or MT526-8 trim tab bending tool bolt to bend tab; do not use tool as a lever. CAUTION Bend tab upward only when absolutely necessary; bending tab upward can increase rotor vibration. CAUTION MT526-1 trim tab bending tool (for A016-4 [stainless steel skin] blades) and MT526-8 trim tab bending tool (for A016-6 [aluminum skin] blades) are not interchangeable. Use of wrong bending tool can result in blade damage. MT090-1 trim tab bending tool (for earlier blades) is obsolete. 1. Using felt tip marker, ink mark main rotor blade trim tab per Figure 10-13. Mark line with a measuring point in the center of the tab (approximate). 2. Position MT352-1 gage chordwise across blade upper surface and tab trailing edge. Zero dial indicator on measuring point. 3. Position MT526-1 (trim tab bending tool (for A016-4 [stainless steel skin] blades) or MT526-8 trim tab bending tool (for A016-6 [aluminum skin] blades) on tab per Figure 10-12. Slide tool completely over tab until tool stops contact blade trailing edge. Double-rib side of tool should contact tab upper surface to bend tab down. Double-rib side of tool should contact tab bottom surface to bend tab up. 4. Tighten MT526 bending tool bolt to bend tab. Make slight bends and re-measure tab with MT352-1 gage. Bend trim tab 0.015 inch (down) to effect dynamic movement of main rotor blade tip approximately 0.2 inch (downward). NOV 2020 Chapter 10 Rigging, Track and Balance Page 10.32G ROBINSON MAINTENANCE MANUAL R22 SERIES Intentionally Blank Page 10.32H Chapter 10 Rigging, Track and Balance NOV 2020 ROBINSON MAINTENANCE MANUAL R22 SERIES ROBINSON MAINTENANCE MANUAL MODEL R22 10.234 Main Rotor Track and Balance Troubleshooting The following are some of the symptoms and corrections which occur in the Track and Balance operations of the helicopter. Decide on the various causes of a given trouble and then eliminate causes one by one, beginning with the most probable. 1. Symptom Excessive Cyclic Stick Shake 2. Excessive Ship Vibration Issued 5/22/87 Probable Cause Main Rotor Out of Track or Balance Rough or Binding A205-3 Fork Assy (Upper Swash- plate) Brinelled Spindle Bearings (rough movement) Blade surface rough (chipped) paint Rough or Binding Pitch Links M.R. Blade Boot Misaligned M.R. Hub Teeter or Coning Hinge Binding M.R. Blade Trim Tabs Bent Upward Blade Match Main Rotor out of Track and Balance M.R. Hub Teeter or Coning Hinge Friction Improperly Adjusted Sticky Coning Hinge Bearings in M.R. Hub Correction Track and Balance with Chadwick-Helmuth Balanc- ing Equipment Replace or refer to Section 8.6 of Mainte- nance Manual RHC replacement of Spindle Bearings Feather in rough edges or repaint Replace nitch link rod ends for smooth operation Replace boot or realign. Boot should show deformation as cyclic and collective are moved through their normal arc or travel. RHC replacement or rework for smooth operation Bend Trim Tabs down evenly RHC reulacement of blade(s) Track and Balance with Chadwick-Helmuth Balanc- ing Equipment Refer to Section 9.123 of Maintenance Manual RHC replacement or refer to Section 9.123 Page 10.33 ROBINSON MAINTENANCE MANUAL MODEL R22 10.234 Main Rotor Track and Balance Troubleshooting (cont'd) 2. 3. 4. 5. 6. Page 10.34 Symptom Excessive Ship Vibration (cont'd) Excessive Cyclic Stick Forces Intermittent Blade Track Picture Radical Changes to Cylic Trim Lateral Inter- mittent Aircraft Vibration Probable Cause Brinelled Spindle Bearings (rough movement) Worn Teeter Bearing in M.R. Hub Brinelled Spindle Bearings (rough movement) M.R. Blade Trim Tabs Bent Upward M.R. Hub Teeter or Coning Hinge Friction Improperly Adjusted Sticky Coning Hinge Bearings in M.R. Hub Teeter Hinge not Broken-In Brinelled Snindle Bearings (rough movement) Worn Teeter Hinge Bearings in M.R. Hub Brinelled Spindle Bearings (rough movement) Engine misfiring due to malfunction in soark- plugs, ignition ieads, magneto or engine not broken-in • Correction RHC replacement of Spindle Bearing RHC replacement of M.R. Hub Bearings RHC replacement of Spindle Bearings Bend Trim Tabs down evenly Refer to Section 9.123 RHC replacement or refer to Section 9.123 Adjust track to minimize error RHC replacement of Spindle Bearings RHC replacement of M.R. Hub Bearings RHC replacement of Spindle Bearings Refer to Lycoming Maintenance Instructions Issued 5/22/87 ROBINSON MAINTENANCE MANUAL MOCELR22 10.240 Tail Rotor Balance Procedure Refer to specific manufacturer's installation instructions when using balancing equipment other than Chadwick-Helmuth 177- or 8350- series Vibrex system. Install Chadwick-Helmuth equipment per Section 10.222. Set Function Knob on Balancer to appropriate channel. Set balancer RPM Range knob to X10 and set RPM to 340. With helicopter running, with governor ON, view tail rotor assembly with Strobex. Tune Balancer while viewing target tape and adjusting RPM dial on Balancer. Record clock angle and IPS on tail rotor balance chart. Adjust as required until balance is less than 0.2 IPS. WARNING Both tail rotor blades must be same part number Spanwise balance adjustments for A029-1 square-tip blades made by adding, subtracting, or exchanging weights under the removable tip cover. Use A 134-1 or -2 tip weights or AN960~8 or -SL washers. -SL washers may be trimmed as a very fine adjustment. Span wise balance for A029-2 round-tip blades are made by exchanging different diameter washers under nut securing blade's outboard retaining bolt. The bolt has sufficient length to allow necessary span wise weight changes; verify 2-4 threads protruding past nut after torquing per Section 1.320. Chord wise balance is adjusted by adding, subtracting, or exchanging A 141-14, A214-3, AN960-416 or -416L washers under nut securing blade's pitch link attaching bolt. Change pitch link, attaching bolt length as required for proper thread engagement (see Section 1.300, refer to IPC for allowable lengths). Change 23: JAN 2005 Page 10.35 ROBINSON MAINTENANCE MANUAL A008-2 TAIL ROTOR (WITH A029-1 SQUARE-TIP BLADES) TRACK AND BALANCE CHART ----- TARGET BLADE REFLECTIVE ~ TARGET REFLECTIVE TARGET MOUNTED OPPOSITE ANY CHORD WEIGHT PREVIOUSLY INSTALLED ~--- BLANK BLADE CHORDWISE WEIGHTS MO □ ELR22 SHIP S/N ---- DATE ------ HOURMETER 1 SPANWISE WEIGHTS 3 ADD TO BLANK 2 AN960-8L WASHERS S 1 p 0 A N w I s (2)AN960-416L WASHERS= (l)AN960-416 WASHER (3.5)AN960-416L WASHERS= (l)A214-3 WASHER (5)AN960-416L WASHERS= (l)Al41-14 WASHER (2)AN960-8L WASHERS= (l)AN960-8 WASHER (8)AN960-8L WASHERS= (l)Al34-l WEIGHT RUN CLOCK IPS CHANGE MADE BEFORE NEXT RUN FIGURE 10-14 Page 10.36 Change 23: JAN 2005 ROBINSON MAINTENANCE MANUAL MODELR22 A008-4 TAIL ROTOR SHIP S/N ---- DATE (WITH A029-2 ROUND-TIP BLADES) TRACK AND BALANCE CHART ------ -TARGET BLADE REFLECTIVE TARGET ~LECTIVE TARGET MOUNTED OPPOSITE ANY CHORD WEIGHT PREVIOUSLY INSTALLED --BLANK RUN BLADE MOUNT ACCELEROMETER ON GEARBOX WITH CON- NECTOR POINTED UP. CLOCK IPS ~\,,'y,..~'{.. 'f. ~\)\) '\\J<:)~ '\'y,..~\:}~:~i' ~~<:)~ ~ ~i;,: ~<:J~s x<:Jf),:i?.: I\ ~s '\(),°> ~'y,..s'\ ?., WEIGHTS HOURMETER (2)NAS1149FO432P WASHERS= (l)NAS1149FO463P WASHER (3.5)NAS1149FO432P WASHERS= (l)A214-3 WASHER (3)NAS1149FO463P WASHERS= (l)Al41-14 WASHER (6.5)NAS1149FO463P WASHERS= (l)AN97O-4 WASHER *A MINIMUM OF ONE NAS1149FO432P WASHER MUST BE INSTALLED IN CHORDWISE LOCATION ON EACH BLADE. CHANGE MADE BEFORE NEXT RUN FIGURE 10-14A ---- 0 N w Change 23: JAN 2005 Page 10.37 ROBINSON MAINTENANCE MANUAL MODELR22 10.250 Autorotational RPM Adjustment Use the following procedure for checking and adjusting autorotational RPM: WARNING Failure to properly adjust autorotational RPM (RPM too low) may prevent the rotorcraft from achieving proper RPM at low gross weights. 1. Perform autorotation RPM check at minimum practical weight. Calculate the takeoff gross weight of the helicopter. Record the time on the hour meter. Take-Off gross weight Take-Off hourmeter reading 2. Set the altimeter to 29.92" Hg ( 1013.2 millibars) prior to performing the autorotation. Autorotate with the collective control firmly held against the down stop with an airspeed of 50 KIAS. WARNING Do not allow the rotor to overspeed when performing autorotation checks. Progressively lengthen both main rotor pitch link rod ends until full down collective can be obtained without over-speeding the rotor. Take at least 3 RPM readings at 500 to 1000 foot altitude intervals. Record the following in-flight data: Test# Hourmeter OAT Pressure Test Reading Altitude % RPM 1 2 3 4 5 Page 10.38 Change 23: JAN 2005 ROBINSON MAINTENANCE MANUAL MODELR22 10.250 Autorotational RPM Adjustment (cont'd) 3. After each flight, refer to figure 10-15 and determine the following: Elapsed Time Test Gross (in-flight Pounds of Weight RPM Test hourmeter Fuel (take-off gross Chart% Test% RPM Correction reading minus Consumed (from in-flight (chart% RPM # 1 2 3 4 5 weight RPM take-off (elapsed time minus fuel data) minus Test% hourmeter x 45 lbs/hr) consumed RPM) reading) 4. Adjust the pitch links based on the average RPM correction required. Lengthen both pitch links to decrease RPM if the test RPM is greater than the chart RPM (lengthening the pitch links one full rod end turn will reduce RPM 3%}. Shorten both pitch links to increase RPM. Be sure to adjust both pitch links exactly the same so track will not be affected. 5. Repeat steps (a) through (d) as required until the RPM correction is ± 1 % of chart RPM. Determine chart RPM as follows: a. Start at outside air temperature, and draw a vertical line up to the pressure altitude. b. Draw a horizontal line from the pressure altitude to the rotorcraft gross weight at time of autorotation. c. Draw a vertical line down from the gross weight to the required autorotation RPM. d. Make adjustment to the main rotor pitch links as required to obtain test autorotation RPM within ± 1 % of chart RPM (see Figure 10-15). Change 23: JAN 2005 Page 10.39 ""'O 0) co co ..... 0 .j:::,. 0 0 :::J" 0) :J co co N w c_ ► z N 0 0 01 .,, - G') C :x, m ~ 0I ~ (J1 2 0 18 16 f-< N N 14 L,, 0 g 12 .... X N 10 Q ;:) f-< ~ 8 ....1 < ~ 6 f-< U) z 4 ~l Q 2 0 I I I I I I I I I I I I ; I I I I I I I I I I I -40 -20 0 20 40 60 BO TEMPEnA TUTU:::, DEGREES F I I I I 100 AUTOROTATION RPM___ COLLECTIVE fULL DOWN 50 KIAS (One full turn of rod ends= 3% RPM) (One full turn of rod end= two turns of the barrel) 98 100 102 104 106 108 110 112 % RPM (Example: OAT=23°C, llp=2000', W=l050 lbs, RPM= 99.5%.) IJ 0 m -z m 0 z s: ~ z-t m z)> z n m s: )> z ~r s: 0 C m r D IU IU